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公开(公告)号：US20240352869A1
公开(公告)日：2024-10-24
申请号：US18137756
申请日：2023-04-21
发明人： Scott Goyette , Janet Shaw , Gregory S. Hagen , David L. Lincoln , Zaffir A. Chaudhry , Danbing Seto
CPC分类号： F01D21/003 , B64D27/10 , H04N23/90 , F05D2260/83
摘要： An assembly for an aircraft propulsion system includes a propulsor section for the aircraft propulsion system, a plurality of imaging devices, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The plurality of imaging devices are mounted in the propulsor section. Each imaging device includes a camera. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the camera of each imaging device of the plurality of imaging devices to capture image data of each propulsor blade of the plurality of propulsor blades and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data from the camera of two or more imaging devices of the plurality of imaging devices.
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公开(公告)号：US12123309B2
公开(公告)日：2024-10-22
申请号：US18485980
申请日：2023-10-12
申请人： RTX Corporation
发明人： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis , Nathan L. Messersmith
IPC分类号： F01D15/10 , B64D27/02 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/18 , H02K7/20 , H02K11/00
CPC分类号： F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/1823 , H02K7/20 , H02K11/0094 , B64D27/026 , F05D2220/50 , F05D2220/76
摘要： An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.
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公开(公告)号：US20240344487A1
公开(公告)日：2024-10-17
申请号：US18675233
申请日：2024-05-28
发明人： David Marion Ostdiek , Alan Roy Stuart , David Alan Niergarth , Gert Johannes van der Merwe , Brandon Wayne Miller , Stephen William Freund
摘要： A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.
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公开(公告)号：US20240343399A1
公开(公告)日：2024-10-17
申请号：US18298952
申请日：2023-04-11
发明人： Martin Amari , Xin Wu , Tyler W. Hayes
CPC分类号： B64D27/24 , B60L3/12 , B60L50/60 , B64D27/10 , B64D31/00 , B64D45/00 , B60L2200/10 , B64D27/026 , B64D2045/0085
摘要： A hybrid electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an electric motor configured to drive the propulsor. A controller is in signal communication with the gas turbine engine and the electric propulsion system. The controller operates the gas turbine engine based on an on-board engine model (OEM), monitors electrical parameters of the electric propulsion system, and updates the OEM in response to changes to the electrical parameters.
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公开(公告)号：US20240326609A1
公开(公告)日：2024-10-03
申请号：US18576512
申请日：2022-07-05
发明人： Djemouai HADJIDJ
CPC分类号： B60L50/10 , B64D27/026 , B64D27/10 , B64D27/24 , H02J3/46 , B60L2200/10 , B60L2210/20 , B60L2220/42 , B64D2221/00 , H02J2310/44
摘要： Electrical architecture for an aircraft with thermal/electrical hybrid propulsion, comprising, for each turbine engine:
an aeroplane AC electrical network,
at least one first electrical machine mechanically coupled to a high-pressure shaft of the turbine engine;
at least one second electrical machine mechanically coupled to a low-pressure shaft of the turbine engine;
a reversible AC/AC electrical energy conversion module;
switch elements; and
an electronic system for controlling the conversion module and the switch elements, configured to put the architecture;
in at least one so-called “power distribution hybridisation” operating mode corresponding to a first configuration of the switch elements in which the at least one second machine is coupled to the aeroplane network and at least one first machine is coupled to the aeroplane network via the electrical energy conversion module.-
公开(公告)号：US12103696B2
公开(公告)日：2024-10-01
申请号：US17721200
申请日：2022-04-14
发明人： Bradley Passe , Kip Campbell
CPC分类号： B64D35/00 , B64C29/0033 , B64D27/10 , B64D27/16
摘要： An aircraft includes a fuselage, a pylon, a wing positioned between the fuselage and the pylon, and a plurality of drive shafts located inside the wing and adapted to drive a rotor associated with the pylon.
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公开(公告)号：US20240301832A1
公开(公告)日：2024-09-12
申请号：US18181159
申请日：2023-03-09
发明人： Bahram Jadidian , Kevin Blinn , Mehrad Mehr
摘要： Components of gas turbine engines, aircraft comprising the components, and methods of producing the components are provided. The component includes a surface, and a set of tiles secured to the surface at interfaces between the set of tiles and the surface and between each of the set of tiles. The set of tiles conform to the surface and in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating.
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公开(公告)号：US12084195B2
公开(公告)日：2024-09-10
申请号：US17377551
申请日：2021-07-16
发明人： Aaron M. Finke , Michael R. Blewett
摘要： A dual drive, dual clutch accessory drive system for an aircraft including a first input shaft connected to a first pressure spool of a turbine engine. The first input shaft rotates at a first speed. A second input shaft is connected to a second spool of the turbine engine that is distinct from the first spool. The second input shaft rotates at a second speed. An output shaft operatively connected to an aircraft accessory. A first drive path selectively operatively connects the first input shaft with the output shaft. The first drive path includes a first clutch. The first drive path being operable to rotate the output shaft at the first speed. A second drive path operatively connects the second input shaft with the output shaft. The second drive path includes a second clutch. The second drive path is operable to rotate the output shaft at the second speed.
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公开(公告)号：US12078353B2
公开(公告)日：2024-09-03
申请号：US18058755
申请日：2022-11-24
发明人： Etienne Plamondon
摘要： A method of operating an aircraft power plant having an interburner fluidly connected between a combustion engine and a turbine, includes: operating the combustion engine at an air-fuel ratio corresponding to a nominal air-fuel ratio to generate combustion gases; receiving the combustion gases generated by the combustion engine into the interburner; increasing a temperature of the combustion gases generated by a combustion chamber of the combustion engine by lowering the air-fuel ratio to an ignition air-fuel ratio lower than the nominal air-fuel ratio; injecting fuel into the interburner to cause ignition of a mixture of the combustion gases and the fuel received into the interburner; and after ignition of the interburner, increasing the air-fuel ratio above the ignition air-fuel ratio.
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公开(公告)号：US12065937B1
公开(公告)日：2024-08-20
申请号：US18394669
申请日：2023-12-22
申请人： RTX Corporation
CPC分类号： F01D17/14 , B64D27/10 , B64D33/04 , F01D17/16 , F05D2220/323 , F05D2250/90
摘要： A variable area nozzle assembly includes a fixed center plug, a fixed outer nozzle, and an inner nozzle. The fixed center plug includes a plug body and a protrusion. The fixed outer nozzle extends about the fixed center plug. The inner nozzle extends about the fixed center plug. The inner nozzle is disposed between the fixed center plug and the fixed outer nozzle. The inner nozzle forms a primary duct between the inner nozzle and the fixed outer nozzle. The primary duct includes an exit plane. The inner nozzle body forms a secondary duct and a gap. The gap is a nozzle outlet of the secondary duct. The gap includes a gap inlet and a gap outlet. The gap inlet is disposed upstream of the protrusion. The gap outlet is disposed downstream of the protrusion. The inner nozzle body is translatable between a first position and a second position. In the first position, the primary duct has a first area at the exit plane and the inner nozzle body is disposed at the protrusion. In the second position, the primary duct has a second area at the exit plane and the inner nozzle body is spaced from the protrusion.
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